EP4134530B1 - Entraînement à modulation de largeur d'impulsion pour collecteurs de carburant étagés - Google Patents

Entraînement à modulation de largeur d'impulsion pour collecteurs de carburant étagés

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Publication number
EP4134530B1
EP4134530B1 EP22190228.1A EP22190228A EP4134530B1 EP 4134530 B1 EP4134530 B1 EP 4134530B1 EP 22190228 A EP22190228 A EP 22190228A EP 4134530 B1 EP4134530 B1 EP 4134530B1
Authority
EP
European Patent Office
Prior art keywords
fuel
flow
metering mechanism
primary
controller
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP22190228.1A
Other languages
German (de)
English (en)
Other versions
EP4134530A1 (fr
Inventor
Lu XUENING
Ezzat MESHKINFAM
Sean DURAND
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Pratt and Whitney Canada Corp
Original Assignee
Pratt and Whitney Canada Corp
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Filing date
Publication date
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Publication of EP4134530A1 publication Critical patent/EP4134530A1/fr
Application granted granted Critical
Publication of EP4134530B1 publication Critical patent/EP4134530B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/32—Control of fuel supply characterised by throttling of fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
    • F02C3/22—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/222—Fuel flow conduits, e.g. manifolds
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/228—Dividing fuel between various burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/232—Fuel valves; Draining valves or systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/263—Control of fuel supply by means of fuel metering valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/40—Control of fuel supply specially adapted to the use of a special fuel or a plurality of fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/85—Starting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/05—Purpose of the control system to affect the output of the engine
    • F05D2270/051—Thrust
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/05—Purpose of the control system to affect the output of the engine
    • F05D2270/053—Explicitly mentioned power
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/301—Pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/301—Pressure
    • F05D2270/3015—Pressure differential pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/303—Temperature
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/306—Mass flow

Definitions

  • the present disclosure relates to fuel control for gaseous fuel in staged manifolds, for example in an aircraft engine.
  • Gas turbine engines typically burn liquid fuel (e.g. kerosene) and use on/off staging for turn-down and startup, for example using two manifolds, which does not easily translate to gaseous fuels. Therefore there is always a need in the aerospace industry for more precise control of gaseous fuel flow in gas turbine engines.
  • liquid fuel e.g. kerosene
  • on/off staging for turn-down and startup, for example using two manifolds, which does not easily translate to gaseous fuels. Therefore there is always a need in the aerospace industry for more precise control of gaseous fuel flow in gas turbine engines.
  • a prior art fuel system having the features of the preamble of claim 1 is disclosed in US 2003/217545 A1 .
  • Another prior art fuel system is known from US 2005/241318 A1 .
  • a method for operating a proportional flow valve is disclosed in WO 02/05046 A2 .
  • the controller is operable to control the secondary fuel flow valve to pulse a flow of fuel passing therethrough in pulse width modulation (PWM) pulses at a low end of a fuel flow range for the secondary manifold.
  • PWM pulse width modulation
  • the controller can be an electronic engine control (EEC) of a gas turbine engine.
  • a position feedback sensor is operatively connected to the fuel metering mechanism and operable to generate a signal indicative of a position of the fuel metering mechanism.
  • the controller is operatively connected to the position sensor.
  • the controller is operable to control the position of the fuel metering mechanism based on the signal indicative of the position of the fuel metering mechanism.
  • a downstream pressure sensor is disposed in the main inlet feed conduit at an inlet of a flow divider assembly downstream of the fuel metering mechanism operable to generate a signal indicative of a fuel pressure at the inlet of the flow divider assembly.
  • the controller is operatively connected to the downstream pressure sensor and operable to receive the signal from the downstream pressure sensor.
  • the controller is operable to control the fuel metering mechanism to act as a pressure regulator in low flow operating conditions.
  • the controller includes machine readable instructions to cause the controller to place the primary fuel control valve and the secondary fuel flow valve in respective closed positions, pressurize the main inlet feed conduit feeding the primary and secondary fuel flow valve valves with gaseous fuel, place the primary fuel flow valve into its open condition to supply the gaseous fuel to fuel injectors of the primary manifold downstream from the primary fuel flow valve, and modulate the primary fuel flow valve between its open and closed position to pulse a flow of gaseous fuel passing therethrough in pulse width modulation (PWM) pulses at a low end of a fuel flow range for the primary manifold.
  • PWM pulse width modulation
  • the controller includes machine readable instructions to cause the controller to schedule a PWM dwell time relative to sensed engine conditions, and schedule a position of the fuel metering mechanism relative to a sensed pressure at an inlet of a flow divider assembly.
  • the sensed engine conditions derive from signals indicative of at least one of: the pressure at the inlet of the fuel metering mechanism, the pressure drop across the fuel metering mechanism, the temperature of the gaseous fuel at the outlet of the fuel metering mechanism, and/or the position of the fuel metering mechanism.
  • the sensed pressure at the inlet of the flow divider assembly is derived from a signal indicative of the pressure at the inlet of the flow divider assembly.
  • the controller includes machine readable instructions to cause the controller to modulate the secondary fuel flow valve between its open and closed position to pulse a flow of gaseous fuel passing therethrough in pulse width modulation (PWM) pulses at a low end of a fuel flow range for the secondary manifold to prevent surge or notch when placing the secondary fuel flow valve its opened position.
  • PWM pulse width modulation
  • the method includes modulating the secondary fuel flow valve between its open and closed position to pulse a flow of gaseous fuel passing therethrough in pulse width modulation (PWM) pulses at a low end of a fuel flow range for the secondary manifold to prevent surge or notch when placing the secondary fuel flow valve its opened position.
  • PWM pulse width modulation
  • the sensed engine conditions derive from signals indicative of at least one of: a pressure at an inlet of the fuel metering mechanism, a pressure drop across the fuel metering mechanism, a temperature of the gaseous fuel at an outlet of the fuel metering mechanism, and/or a position of the fuel metering mechanism.
  • the method includes, controlling a position of the fuel metering mechanism and the PWM pulses of the first and second flow valves based on the plurality of sensed inputs.
  • the sensed pressure at the inlet of the flow divider assembly is derived from a signal indicative of the pressure at the inlet of the flow divider assembly.
  • the method further includes, controlling the fuel metering mechanism to act as a pressure regulator in low flow operating conditions based on the sensed input.
  • FIG. 1 an illustrative view of an embodiment of a system in accordance with the disclosure is shown in Fig. 1 and is designated generally by reference character 100.
  • FIG. 2 Other embodiments and/or aspects of this disclosure are shown in Fig. 2 .
  • Certain embodiments described herein can be used to improve control of gaseous fuel flow in a gas turbine engine.
  • the present disclosure relates generally to fuel control for gas turbine engines, and more particularly to control of gaseous fuel flow.
  • a gas turbine engine may be fueled with gaseous fuel such as hydrogen gas. It is possible to gasify liquid hydrogen from an aircraft supply through an appropriate fuel pump, heat exchangers, pressure regulator, and metering valves. It is desired to control gaseous fuel delivery to the engine such that stable and responsive control over the wide range of flow conditions would be maintained.
  • the typical fuel control for aircraft engines is designed for purely liquid fuel flow. Liquid fuel is an incompressible fluid, whereas gaseous fuel is compressible.
  • the full fuel system can include a combination of liquid and gaseous hydrogen, meaning the fuel control system needs to control both compressible and incompressible flows.
  • Gas turbine engines typically burn liquid fuel (e.g. kerosene) and use on/off staging for turn-down and startup, for example using two manifolds, which does not easily translate to gaseous fuels.
  • liquid fuel e.g. kerosene
  • high turn down ratio can render control of the gaseous flow in a low flow regime particularly challenging, for example exposing the engine to a risk of flame out or surging as a result of inaccurate fuel flow supply.
  • the pressure supplied to the fuel line P1 is regulated at a much higher pressure of the burner pressure P3 (e.g. at least double). Therefore, variation of fuel metering valve output sets a variable throat area to the valve which is maintained choked (e.g. in a sonic state) at all system flow conditions.
  • the aircraft fuel system includes one or more controllable flow valves which can be used to manage and maintain the distribution of the gas flow into the engine (e.g. the fuel manifolds) during starting and large transient maneuvers.
  • the system introduces the ability to actively control the gaseous flow distribution between the primary and secondary manifolds.
  • the fuel used for combustion is a compressible media.
  • an aircraft 1 can include an engine 100, where the engine 100 can be a propulsive energy engine (e.g. creating thrust for the aircraft 1), or a non-propulsive energy engine, and a fuel system.
  • the engine 100 is a turbofan engine, although the present disclosure may likewise be used with other engine types.
  • the engine 100 includes a compressor section 102 having a compressor 104 in a primary gas path 106 to supply compressed air to a combustor 108 of the aircraft engine 100.
  • the primary gas path 106 includes a nozzle manifold 110 for issuing fluid to the combustor 108.
  • the primary gas path 106 includes, in fluid communication in a series: the compressor 104, the combustor 108 fluidly connected to an outlet 114 of the compressor 104, and a turbine section 116 fluidly connected to an outlet 118 of the combustor 108.
  • the turbine section 116 is mechanically connected to the compressor 104 to drive the compressor 104.
  • the combustor 108 includes a plurality of fuel nozzles 120 (e.g. including a primary set 120a and a secondary set 120b) fluidly connected to the fuel manifold 110, where the primary set 120a is fluidly connected to a primary manifold 110, and the secondary set 120b is fluidly connected to a secondary fuel manifold 111.
  • a main inlet feed conduit 122 fluidly connects a gaseous fuel supply 124 to feed a primary manifold feed conduit 110a and to feed a secondary manifold feed conduit 111a.
  • the main inlet feed conduit 122 includes an inlet end 126 and an outlet end 128 to fluidly connect the gaseous fuel supply 124 to the combustor 108 through the plurality of fuel nozzles 120.
  • the gaseous fuel supply 124 can be any suitable gaseous fuel, such as a gaseous pressure and/or temperature regulated fuel supply, which may be or include hydrogen gas.
  • Certain additional components may also be included in fluid communication between the combustor and the gaseous fuel supply in any suitable order or combination, such as a fuel shut off valve 130, a fuel pump 132, a liquid/gaseous fuel evaporator 134, a turbine air cooling heat exchanger 136, a gaseous fuel accumulator 138, a gaseous fuel metering unit 140, a fuel manifold shut off valve 142, and/or additional pressure regulating devices.
  • the pre-pressurized gaseous fuel accumulator 138 can be used as backup supply pressure source.
  • a fuel control system 200 for controlling the flow of fuel to the aircraft engine 100 through the main inlet feed conduit 122 and the plurality of fuel nozzles 120 includes a means for regulating flow through the main inlet feed conduit 122, a means for generating a signal indicative of an engine state or condition, and a controller 144.
  • the controller 144 is operatively connected to the means for regulating flow and to the means for generating a signal to control the means for regulating a signal based on the signal such that the controller is operable to control a state of the means for regulating to achieve a desired power output (e.g. a command from a pilot, autopilot, or drone software for acceleration of the engine 100).
  • a desired power output e.g. a command from a pilot, autopilot, or drone software for acceleration of the engine 100.
  • the means for regulating flow through the main inlet feed conduit 122 includes at least one metering mechanism 146.
  • the means for generating a signal indicative of an engine state or condition can include any suitable means, for example any number and/or combination of pressure sensors, temperature sensors, position sensors, or the like, disposed in the engine 100 and/or main inlet feed conduit 122, and operatively connected as disclosed herein.
  • the fuel metering mechanism 146 is disposed in the main inlet feed conduit 122 between the inlet end 126 and the outlet end 128 and is operable to regulate flow through both the main inlet feed conduit 122 and in certain embodiments the primary fuel manifold 110.
  • the fuel metering mechanism 146 can include all required instrumentation to validate gas fuel flow therethrough relative to a commanded flow.
  • the first fuel manifold 110 can be a primary fuel manifold configured to provide sufficient fuel during low fuel consumption such as during start up
  • the second fuel manifold 111 can be a secondary fuel manifold configured to supplement the primary fuel manifold during high fuel consumption.
  • the engine 100 can use minimum of two fuel manifolds to regulate the gaseous fuel flow and corresponding back pressure over the full operating range of the engine 100.
  • the primary manifold 100 can be used in starting, to provide a reduced nozzle count which is spread evenly around the engine 100. In applications, the reduced nozzle count can allow for a greater control of the gas flow being introduced through an increased restriction/back pressure, and can reduce the risk of over fueling on start.
  • the secondary manifold 111 is added to provide additional flow at the same gaseous supply pressure if needed or desired.
  • Fuel flow to the first and second fuel manifolds 110, 111 is controlled by a primary controlled flow valve 150 disposed in the first fuel manifold feed conduit 110a, and a secondary controlled flow valve 152 disposed in the second fuel manifold feed conduit 111a.
  • the primary and secondary fuel flow valves 150, 152 each have an open condition operative to permit flow of fuel through the primary manifold feed conduit 122 and a closed condition operative to inhibit (e.g. reduce or completely block) flow of fuel through the primary manifold feed conduit 122.
  • the first and second controlled flow valves 150, 152 can be any suitable controllable flow valve, such as solenoid valves operatively connected to a controller to selectively energize and de-energize the first and second flow valves 150, 152 to selectively allow flow through the first and second manifolds 110, 111 to the combustor 108. While two active valves 150, 152 are shown, it is contemplated that only the primary flow valve 150 can be an actively controlled valve and the secondary valve 152 can be passive. In certain embodiments, valves 150, 152 can be or include a globe valve, or a variable opening, electrically actuated valve.
  • valves 150, 152 can be a calibrated mechanical regulating valve, and once calibrated, provide a similar response and effect.
  • first and second controlled flow valves 150, 152 can be electrohydraulic servo valves operatively connected to the controller 144 to operate in a similar manner to provide a similar response and effect.
  • the controller 144 is operatively connected to control at least the primary fuel flow valve 150 to pulse a flow of gaseous fuel passing therethrough in pulse width modulation (PWM) pulses at a low end of a fuel flow range for the primary manifold 110.
  • PWM control of the flow valve 150 can allow for high precision flow control even at low flow engine states.
  • the same or a similar technique can still be beneficial to the secondary flow valve 152 in other engine states, even if the secondary fuel flow valve 152 remains closed during startup.
  • the controller 144 can include any suitable controller, for example an electronic engine controller (EEC).
  • EEC electronic engine controller
  • the controller 144 can be or include both hard wired circuits that cause a logic to be executed, and/or software-based components, for example, simple electric circuits employing analog sensors and/or components, or the controller 144 can include a CPU, a memory, machine readable instructions in the memory that when executed cause the CPU to perform a method.
  • the controller 144 automatically controls the fuel flow valves 150, 152 and a fuel metering mechanism 146 (e.g. without user input).
  • the controller 144 is operable to collect and process signals from a plurality of inputs, including for example, a downstream temperature, an upstream and downstream pressure, and a delta pressure across the fuel metering mechanism to use and calculate a fuel flow schedule.
  • a fuel pressure sensor 154 (e.g. an absolute pressure) is operatively connected to an inlet of the fuel metering mechanism 146 and operable to generate a signal 155 indicative of the upstream fuel pressure at the inlet of the fuel metering mechanism 146.
  • the controller 144 is operatively connected to the fuel pressure sensor and operable to receive the signal 155 from the fuel pressure sensor 154.
  • the upstream pressure, and its respective signal 155 can have two functions for the controller 144 and fuel metering mechanism 146. First, the controller 144 can use the upstream pressure for validating that the inlet pressure of the fuel metering mechanism 146 is sufficient for operation at the intended operating condition (e.g. start-up or based on the commanded power). Second, the controller 144 can use the upstream pressure for correcting a position of the opening of the fuel metering mechanism 146 relative to the gaseous fuel compressibility at the rated pressure.
  • a position feedback sensor 148 is operatively connected to the fuel metering mechanism 146 and operable to generate a signal 149 indicative of an actual position of the fuel metering mechanism.
  • the position feedback sensor 148 can be or include any suitable position sensor, for example a linear variable differential transformer (LVDT). Because the accuracy of a valve actuator system (e.g. a torque motor driver) may vary with operating conditions (e.g. fluid temperature, pressure, ambient conditions), a direct measurement of actual position (or rate of change of position) of the fuel metering mechanism 146 allows for a more precise control and calculation of metered flow.
  • LVDT linear variable differential transformer
  • the controller 144 is operatively connected to the position sensor 148, and is therefore is operable to control the position of the electronic metering valve 146 based on the each of the signal indicative of an upstream pressure 155 and the signal 149 of the position of the fuel metering mechanism 146, and in certain embodiments, a command power for a desired power output of the aircraft engine 100 to achieve the desired power output (e.g. as simultaneous inputs).
  • a command power for a desired power output of the aircraft engine 100 to achieve the desired power output (e.g. as simultaneous inputs).
  • a delta pressure sensor 156 is operatively connected to the inlet of the fuel metering mechanism 146 and outlet of the of the fuel metering mechanism 146 and is operable to generate a signal 157 indicative of a pressure drop across the fuel metering mechanism 146.
  • the delta pressure sensor 156 provides the differential pressure across the metering mechanism 146 itself for a given opening position (e.g. in conjunction with the correction factors) and can be used to measure the gas flow rate through the fuel metering mechanism 146, for example.
  • the delta pressure sensor 156 can be a differential pressure sensor connected to a pressure tap the main inlet feed conduit 122 at the inlet and outlet of the fuel metering mechanism 146, the delta pressure sensor 156 itself determining the pressure differential.
  • the delta pressure sensor 156 can be an electronic device connecting to separate absolute pressure sensors located at each of the inlet and outlet of the fuel metering mechanism 146, where the electronic device includes a module of the controller 144 that simply takes the difference between the signals for each individual sensor.
  • the controller 144 is operatively connected to the delta pressure sensor 156 and operable to receive the signal 157 from the delta pressure sensor 156, and is operable to measure a gaseous fuel flow rate through the fuel metering mechanism 146 based on the pressure drop and an adjusted position of the fuel metering mechanism (e.g. the corrected position as described above).
  • a temperature sensor 158 is operatively connected to the outlet of the fuel metering mechanism 146 and operable to generate a signal indicative 159 of a temperature of the gaseous fuel at the outlet of the fuel metering mechanism 146.
  • the temperature sensor 158 measures the gas flow temperature at the outlet of the fuel metering mechanism 146 and can also be used to provide a correction factor for the position of the fuel metering mechanism 146. Because the gas temperature will increase as it passes through the fuel metering mechanism 146 due to the Joule Thomson effect, the temperature correction factor can then be used by the controller 144 to control the position of the fuel metering mechanism 146 as a function of the correction factor.
  • the controller 144 is operatively connected to the temperature sensor 158 and is operable to output a temperature correction factor to control the position of the fuel metering mechanism 146 based on the signal 159 indicative of the temperature of the gaseous fuel flow at the outlet of the fuel metering mechanism 146.
  • a downstream pressure sensor 160 is disposed in the main inlet feed conduit 122 at an inlet (e.g. outlet 128 of main inlet feed conduit 122) of the flow divider assembly 145 downstream of the fuel metering mechanism 146 and upstream of the combustor 108, the sensor 160 being operable to generate a signal 161 indicative of a fuel pressure at the inlet of the flow divider assembly 145.
  • the downstream pressure sensor 160 can be an absolute pressure transducer and can be used in 'open loop' operation, when compressibility of the gaseous fuel may be transient in nature as the supply lines are filled/primed with the gaseous fuel.
  • the downstream pressure sensor 160 allows the controller 144 (e.g.
  • the metering mechanism 146 via signal 161) to control the metering mechanism 146 to be used as secondary pressure regulator to improve the metering accuracy at certain engine conditions (e.g. low flow operating conditions). Additionally, by locating the sensor 160 downstream of the fuel metering mechanism 146, the commanded flow can be trimmed to accommodate for any line losses in between the metering valve and the fuel manifold inlet.
  • the controller 144 is operable to control both the fuel metering mechanism 146 and each of the controllable flow valves 150, 152 by sending the control signal to the metering mechanism 146 and to each of the flow valves 150, 152.
  • the algorithm could be constructed using the functionality as described above in addition to known general engineering principles as applied to the specific characteristics of each particular fuel system to which the technology of the present disclosure is applied.
  • the controller 144 includes machine readable instructions to cause the controller to perform a method, for example, a fuel control method for the gas turbine engine.
  • the method includes placing a primary fuel flow valve (e.g. primary flow valve 150) and a secondary fuel flow valve (e.g. secondary flow valve 152) in respective closed positions, pressurizing a main inlet feed conduit (conduit 122) feeding the primary and secondary fuel flow valves with a flow of gaseous fuel (e.g. from fuel supply 124), placing the primary fuel flow valve into an open condition to supply the flow of gaseous fuel to a first plurality of fuel injectors (e.g. injectors 120a) of a primary fuel manifold (e.g.
  • primary manifold 110a downstream of the primary fuel flow valve, and modulating the primary fuel flow valve between its open and closed position to pulse a flow of gaseous fuel passing therethrough in PWM pulses at a low end of a fuel flow range for the primary manifold.
  • the method includes, scheduling a PWM dwell time relative to sensed engine conditions (e.g. downstream temperature or pressure).
  • dwell time refers to the amount of time the flow valve is in the open position, for example, increasing the PWM dwell time will increase the opening of the fuel flow valve.
  • the method further includes scheduling a position of the fuel metering mechanism relative to a sensed pressure at an inlet of a flow divider assembly (e.g. flow divider assembly 145).
  • the method includes modulating the secondary fuel flow valve between its open and closed position to pulse a flow of gaseous fuel passing therethrough in pulse width modulation (PWM) pulses at a low end of a fuel flow range for the secondary manifold to prevent surge or notch when placing the secondary fuel flow valve its opened position.
  • PWM pulse width modulation
  • both fuel flow valves 150, 152 can be held in the closed position while the fuel metering mechanism 146 is in an open position to allow the priming and pressurization of the main inlet feed conduit 122 to pressurize the conduit 122.
  • the primary flow valve 150 can be moved to the open position to allow gas flow into the primary manifold 100. Priming and/or pre-pressurizing the conduit 122 can ensure the fuel velocity when entering the manifold are sufficiently high to pre-vent flashback of the gaseous fuel upon ignition.
  • the fuel metering mechanism 146 can be adjusted to maintain the required pressure at the inlet of the flow divider assembly 145.
  • the secondary manifold flow valve 152 can be opened to allow gas flow into the secondary manifold 111. Similar to the primary manifold 110, flow into the secondary manifold 111 will occur at a flow divider inlet pressure where the gas pressure will result in a sufficiently high velocity gaseous flow into the secondary manifold 111 to prevent flash back.
  • fuel scheduling can then be solely controlled by the fuel metering mechanism based off of the inputs to the controller 144 (e.g. inputs as described above in addition to pilot command, engine power, engine speed, operating parameters for temperature, pressure, altitude).
  • the gaseous supply 124 is maintained at a sufficiently high pressure to obtain the required gas flow at high power, the low flow operating conditions (i.e. engine start) require a significant pressure drop to be imposed on the fuel to accurately meter the flow. With the fuel in a compressible, gaseous state, this can lead to a loss of fidelity in the metering due to the fuel reaching trans sonic and sonic speeds within the metering valve. With the active control of fuel flow valves 150, 152 in the fuel manifolds 110, 111, it is possible to use the flow divider 145 as a second metering mechanism, allowing the gas pressure to be reduced in steps, restoring some of the fidelity in metering control.
  • the fuel metering mechanism 146 can be scheduled to provide a targeted flow divider inlet pressure which may be higher than the required pressure for the given operating condition.
  • the primary fuel flow valve 150 current can then be pulse width modulated (PWM) by the controller 144, which controls the flow valve's 150, 152 opening time per second, effectively simulating a smaller restriction than if the valves were just set to the wide open position. Therefore, while operating the engine 100, the PWM dwell time can be scheduled relative to the appropriate engine parameters (i.e.

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Claims (15)

  1. Circuit de carburant (200) pour un moteur à turbine à gaz (100) d'un aéronef (1) comprenant :
    un conduit d'alimentation d'entrée principal (122) relié fluidiquement à un conduit d'alimentation de collecteur primaire (110a) et destiné à alimenter un conduit d'alimentation de collecteur secondaire (111a) ;
    un collecteur primaire (110) reliant fluidiquement le conduit d'alimentation de collecteur primaire (110a) à une pluralité d'injecteurs de carburant primaires (120a) ;
    un collecteur secondaire (111) reliant fluidiquement le conduit d'alimentation de collecteur secondaire (111a) à une pluralité d'injecteurs de carburant secondaires (120b) ;
    une soupape d'écoulement de carburant primaire (150) disposée dans le conduit d'alimentation de collecteur primaire (110a),
    dans lequel la soupape d'écoulement de carburant primaire (150) présente un état ouvert servant à permettre un écoulement de carburant à travers le conduit d'alimentation de collecteur primaire (110a) et un état fermé servant à empêcher un écoulement de carburant à travers le conduit d'alimentation de collecteur primaire (110a) ;
    une soupape d'écoulement de carburant secondaire (152) disposée dans le conduit d'alimentation de collecteur secondaire (111a), dans lequel la soupape d'écoulement de carburant secondaire (152) présente un état ouvert servant à permettre un écoulement de carburant à travers le conduit d'alimentation de collecteur secondaire (111a) et un état fermé servant à empêcher un écoulement de carburant à travers le conduit d'alimentation de collecteur secondaire (111a) ; et
    un dispositif de commande (144) relié de manière opérationnelle pour commander la soupape d'écoulement de carburant primaire (150),
    dans lequel le dispositif de commande (144) sert à commander la soupape d'écoulement de carburant primaire (150) afin de pulser un écoulement de carburant passant à travers celle-ci en impulsions de modulation par impulsion de durée variable (PWM) au niveau d'une extrémité inférieure d'une plage d'écoulement de carburant pour le collecteur primaire (110) ; et
    caractérisé en ce que
    le circuit de carburant (200) comprend en outre une source de carburant gazeux (124) qui définit une extrémité d'entrée (126) du conduit d'alimentation d'entrée principal (122) afin de fournir du carburant gazeux au collecteur de carburant primaire (110) par l'intermédiaire du conduit d'alimentation d'entrée principal (122), et un mécanisme de dosage de carburant (146) disposé dans le conduit d'alimentation d'entrée principal (122) servant à réguler un débit à travers à la fois le conduit d'alimentation d'entrée principal (122) et le collecteur de carburant primaire (110).
  2. Circuit de carburant (200) selon la revendication 1, dans lequel le dispositif de commande (144) sert à commander la soupape d'écoulement de carburant secondaire (152) afin de pulser un écoulement de carburant passant à travers celle-ci en impulsions de modulation par impulsion de durée variable (PWM) au niveau d'une extrémité inférieure d'une plage d'écoulement de carburant pour le collecteur secondaire (111).
  3. Circuit de carburant (200) selon la revendication 1 ou 2, dans lequel le dispositif de commande (144) comporte des instructions lisibles par machine destinées à amener le dispositif de commande (144) à moduler la soupape d'écoulement de carburant secondaire (152) entre ses positions ouverte et fermée afin d'impulser un écoulement de carburant gazeux passant à travers à celle-ci en impulsions de modulation par impulsion de durée variable (PWM) au niveau d'une extrémité inférieure d'une plage d'écoulement de carburant pour le collecteur secondaire (111) de manière à empêcher une surtension ou une encoche lors de la mise de la soupape d'écoulement de carburant secondaire (152) dans sa position ouverte.
  4. Circuit de carburant (200) selon la revendication 1, 2 ou 3, dans lequel le dispositif de commande (144) comporte des instructions lisibles par machine destinées à amener le dispositif de commande (144) à :
    mettre la soupape d'écoulement de carburant primaire (150) et la soupape d'écoulement de carburant secondaire (152) dans des positions fermées respectives ;
    pressuriser le conduit d'alimentation d'entrée principal (122) qui alimente les soupapes d'écoulement de carburant primaire et secondaire (150, 152) avec du carburant gazeux ;
    mettre la soupape d'écoulement de carburant primaire (150) dans son état ouvert afin de fournir le carburant gazeux aux injecteurs de carburant du collecteur primaire (110) en aval de la soupape d'écoulement de carburant primaire (150) ; et
    moduler la soupape d'écoulement de carburant primaire (150) entre ses positions ouverte et fermée afin d'impulser un écoulement de carburant gazeux passant à travers celle-ci en impulsions de modulation par impulsion de durée variable (PWM) au niveau d'une extrémité inférieure d'une plage d'écoulement de carburant pour le collecteur primaire (110).
  5. Circuit de carburant (200) selon la revendication 4, dans lequel le dispositif de commande (144) comporte des instructions lisibles par machine destinées à amener le dispositif de commande (144) à :
    planifier un temps de repos PWM par rapport à des états de moteur détectés ; et
    planifier une position du mécanisme de dosage de carburant (146) par rapport à une pression détectée au niveau d'une entrée d'un ensemble diviseur de débit (145),
    dans lequel, optionnellement, les états de moteur détectés dérivent de signaux (149, 155, 157, 159) indicatifs d'au moins l'une parmi : une pression au niveau d'une entrée du mécanisme de dosage de carburant (146), une chute de pression à travers le mécanisme de dosage de carburant (146), une température du carburant gazeux au niveau d'une sortie du mécanisme de dosage de carburant (146), et/ou une position du mécanisme de dosage de carburant (146), et dans lequel la pression détectée au niveau de l'entrée de l'ensemble diviseur de débit (145) est dérivée d'un signal (161) indicatif de la pression au niveau de l'entrée de l'ensemble diviseur de débit (145).
  6. Circuit de carburant (200) selon une quelconque revendication précédente, comprenant en outre : un capteur de pression de carburant (154) relié de manière opérationnelle à une entrée du mécanisme de dosage de carburant (146) et servant à générer un signal (155) indicatif d'une pression de carburant au niveau de l'entrée du mécanisme de dosage de carburant (146), dans lequel le dispositif de commande (144) est relié de manière opérationnelle au capteur de pression de carburant (154) et servant à recevoir le signal (155) à partir du capteur de pression de carburant (154), dans lequel le dispositif de commande (144) sert à valider si une pression d'entrée est suffisante pour un fonctionnement dans les états de fonctionnement prévues et/ou pour ajuster une position du mécanisme de dosage de carburant (146) par rapport à une compressibilité de carburant gazeux à une pression nominale.
  7. Circuit de carburant (200) selon une quelconque revendication précédente, comprenant en outre : un capteur de rétroaction de position (148) relié de manière opérationnelle au mécanisme de dosage de carburant (146) et servant à générer un signal (149) indicatif d'une position du mécanisme de dosage de carburant (146) ; et dans lequel le dispositif de commande (144) est relié de manière opérationnelle au capteur de rétroaction de position (148), dans lequel le dispositif de commande (144) sert à commander la position du mécanisme de dosage de carburant (146) sur la base du signal (149) indicatif de la position du mécanisme de dosage de carburant (146).
  8. Circuit de carburant (200) selon une quelconque revendication précédente, comprenant en outre : un capteur de pression delta (156) relié de manière opérationnelle à l'entrée du mécanisme de dosage de carburant (146) et à la sortie du mécanisme de dosage de carburant (146) et servant à générer un signal (159) indicatif d'une chute de pression à travers le mécanisme de dosage de carburant (146), dans lequel le dispositif de commande (144) est relié de manière opérationnelle au capteur de pression delta (156) et servant à recevoir le signal (157) à partir du capteur de pression delta (156), dans lequel le dispositif de commande (144) sert à mesurer un débit de carburant gazeux à travers le mécanisme de dosage de carburant (146) sur la base de la chute de pression et d'une position ajustée du mécanisme de dosage de carburant (146).
  9. Circuit de carburant selon une quelconque revendication précédente, comprenant en outre : un capteur de température (158) relié de manière opérationnelle au conduit d'alimentation d'entrée principal (122) au niveau de la sortie du mécanisme de dosage de carburant (146) et servant à générer un signal (159) indicatif d'une température du carburant gazeux au niveau de la sortie du mécanisme de dosage de carburant (146), dans lequel le dispositif de commande (144) est relié de manière opérationnelle au capteur de température (158), et dans lequel le dispositif de commande (144) sert à délivrer en sortie un facteur de correction de température et à commander la position du mécanisme de dosage de carburant (146) sur la base du signal (159) indicatif de la température de l'écoulement de carburant gazeux au niveau de la sortie du mécanisme de dosage de carburant (146).
  10. Circuit de carburant selon une quelconque revendication précédente, comprenant en outre un capteur de pression aval (160) disposé dans le conduit d'alimentation d'entrée principal (122) au niveau d'une entrée d'un ou de l'ensemble diviseur de débit (145) en aval du mécanisme de dosage de carburant (146) et servant à générer un signal (161) indicatif d'une pression de carburant au niveau de l'entrée de l'ensemble diviseur de débit (145), dans lequel le dispositif de commande (144) est relié de manière opérationnelle au capteur de pression aval (160) et sert à recevoir le signal (161) à partir du capteur de pression aval (160), dans lequel le dispositif de commande (144) sert à commander le mécanisme de dosage de carburant (146) pour agir comme un régulateur de pression dans des états de fonctionnement à faible débit.
  11. Moteur à turbine à gaz (100) pour un aéronef, le moteur à turbine à gaz (100) comprenant le circuit de carburant (200) selon une quelconque revendication précédente, et ayant, en communication fluidique en série, une section de dispositif combustor (102), un dispositif combustor (108) et une section de turbine (116), dans lequel une sortie (128) du conduit d'alimentation d'entrée principal (122) est reliée fluidiquement au dispositif combustor (108) par l'intermédiaire des collecteurs de carburant primaire et secondaire (110), et dans lequel le dispositif de commande (144) est une commande moteur électronique (EEC) du moteur à turbine à gaz (100).
  12. Procédé de régulation de carburant pour un moteur à turbine à gaz (100) selon la revendication 11, comprenant :
    la mise de la soupape d'écoulement de carburant primaire (150) et de la soupape d'écoulement de carburant secondaire (152) dans des positions fermées respectives ;
    la pressurisation du conduit d'alimentation d'entrée principal (122) qui alimente les soupapes d'écoulement de carburant primaire et secondaire (150, 152) avec un écoulement de carburant gazeux ;
    la mise de la soupape d'écoulement de carburant primaire (150) dans un état ouvert afin de fournir l'écoulement de carburant gazeux à la pluralité d'injecteurs de carburant primaires (120a) du collecteur de carburant primaire (110) en aval de la soupape d'écoulement de carburant primaire (150) ;
    la modulation de la soupape d'écoulement de carburant primaire (150) entre ses positions ouverte et fermée afin d'impulser un écoulement de carburant gazeux passant à travers celle-ci en impulsions de modulation par impulsion de durée variable (PWM) au niveau d'une extrémité inférieure d'une plage d'écoulement de carburant pour le collecteur primaire (110) ;
    la planification d'un temps de repos PWM par rapport à des états de moteur détectés ; et
    la planification d'une position du mécanisme de dosage de carburant (146) par rapport à une pression détectée au niveau d'une entrée d'un ensemble diviseur de débit (145).
  13. Procédé de régulation de carburant selon la revendication 12, comprenant en outre la modulation de la soupape d'écoulement de carburant secondaire (152) entre ses positions ouverte et fermée afin d'impulser un écoulement de carburant gazeux passant à travers à celle-ci en impulsions de modulation par impulsion de durée variable (PWM) au niveau d'une extrémité inférieure d'une plage d'écoulement de carburant pour le collecteur secondaire (111) de manière à empêcher une surtension ou une encoche lors de la mise de la soupape d'écoulement de carburant secondaire (152) dans sa position ouverte.
  14. Procédé de régulation de carburant selon la revendication 12 ou 13, dans lequel les états de moteur détectés dérivent de signaux (149, 155, 157, 159) indicatifs d'au moins l'une parmi : une pression au niveau d'une entrée du mécanisme de dosage de carburant (146), une chute de pression à travers le mécanisme de dosage de carburant (146), une température du carburant gazeux au niveau d'une sortie du mécanisme de dosage de carburant (146), et/ou une position du mécanisme de dosage de carburant (146), et comprenant en outre :
    la commande d'une position du mécanisme de dosage de carburant (146) et des impulsions PWM des soupapes d'écoulement de carburant primaire et secondaire (150, 152) sur la base de la pluralité d'entrées détectées.
  15. Procédé de régulation de carburant selon la revendication 12, 13 ou 14, dans lequel la pression détectée au niveau de l'entrée de l'ensemble diviseur de débit (145) est dérivée d'un signal (161) indicatif de la pression au niveau de l'entrée de l'ensemble diviseur de débit (145), et comprenant en outre :
    la commande du mécanisme de dosage de carburant (146) pour agir comme un régulateur de pression dans des états de fonctionnement à faible débit sur la base de d'entrée détectée.
EP22190228.1A 2021-08-12 2022-08-12 Entraînement à modulation de largeur d'impulsion pour collecteurs de carburant étagés Active EP4134530B1 (fr)

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US11746711B2 (en) 2023-09-05
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US20230050741A1 (en) 2023-02-16

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